An experimental study on transonic swept convex-corner flows

Chung, Kung Ming; Su, Kao Chun

doi:10.1016/j.ast.2018.11.012

Cited by 4 publications

(8 citation statements)

References 19 publications

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“…The interaction region for η = 17 • was greater than that for η = 13 • ; i.e., expanding both upstream and downstream. For a transonic expansion flow (M = 0.83), the flow expanded to supersonic speed and there was SIBLS [6]. The PSP images for λ = 10 • are shown in Figure 5.…”

Section: Surface Pressure Patternmentioning

confidence: 99%

“…The images also show a greater adverse gradient downstream from the corner. An increase in η resulted in an extensio compression process, corresponding to the flow reattachment based on the oil fl alization [6], shown as the solid line in Figure 5c.…”

Section: Surface Pressure Patternmentioning

confidence: 99%

“…At M = 0.64, it is in the subsonic speed regime and there is no flow separation [6]. The pressure distributions in the longitudinal direction using the PSP (5 pixel × 5 pixel) and the Kulite sensors are shown in Figure 6, where the positive value of x* (=x/δ) denotes the non-dimensional distance perpendicular to the corner line.…”

Section: Mean Surface Pressure Distributionmentioning

confidence: 99%

“…The peak value of surface pressure fluctuations reaches approximately 15% of the local mean surface pressure [5]. For a swept convex corner, Chung and Su [6] showed that an increase in the swept angle, λ, results in a delay in the transition from subsonic to transonic expansion flow and in SIBLS. The shock excursion phenomenon is alleviated, resulting in reduced peak pressure fluctuations.…”

Section: Introductionmentioning

confidence: 99%

“…A study by Chung and Su [6] only determined the longitudinal pressure distributions for a swept convex-corner flow using discrete pressure transducers. The spanwise pressure distribution was not addressed.…”

Section: Introductionmentioning

confidence: 99%

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Global Visualization of Compressible Swept Convex-Corner Flow Using Pressure-Sensitive Paint

Chung

Huang

2021

Aerospace

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This study used pressure-sensitive paint (PSP) and determined the surface pressure distributions for a compressible swept convex-corner flow. The freestream Mach numbers were 0.64 and 0.83. The convex-corner angle and swept angle were, respectively, 10–17° and 5–15°. Expansion and compression near the corner apex were clearly visualized. For the test case of shock-induced boundary layer separation, there were greater spanwise pressure gradient and curved shocks. The acquired PSP data agree with the experimental data measured using the Kulite pressure transducers for a subsonic expansion flow. For a transonic expansion flow, the discrepancy was significant. The assumption of a constant recovery factor is not valid in the separation region, and temperature correction for PSP measurements is required.

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Section: Surface Pressure Patternmentioning

confidence: 99%

Section: Surface Pressure Patternmentioning

confidence: 99%

Section: Mean Surface Pressure Distributionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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